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Turbine shroud sealing architecture

Active Publication Date: 2016-06-16
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0004]Accordingly, there is a need for an i

Problems solved by technology

However, the seal is not perfect and it must be ensured to adequately purge the adjacent cavity with sufficient cooling air to avoid hot gas ingestion.

Method used

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  • Turbine shroud sealing architecture
  • Turbine shroud sealing architecture
  • Turbine shroud sealing architecture

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Embodiment Construction

[0013]FIG. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases. A gas path 20 carries the hot combustion gases from the combustor through the turbine section 18 for powering the turbines.

[0014]The combustor 16 is housed in a plenum 17 supplied with compressed air from compressor 14. The turbine section 18 is also surrounded by the plenum 17, defined within the engine case 22, for supplying cooling air to a turbine shroud surrounding the turbine blades 26 (see FIG. 2). The turbine section 18 generally comprises one or more stages of turbine blades 26 extending radially outwardly from respec...

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PUM

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Abstract

A shroud sealing arrangement for a gas turbine engine, which comprises a static shroud assembly mounted to an engine case and having a platform surrounding a rotatable airfoil array. The platform has an inner side and an outer side and extends from a leading edge to a trailing edge. A shroud support structure mounts the shroud platform to the case. A circumferential groove is defined on the outer side of the shroud platform proximal to one of the leading edge and the trailing edge. A sealing ring is set in the groove and adapted to seal cooling air from escaping directly to the gas path.

Description

TECHNICAL FIELD[0001]The application relates generally to gas turbine engines and, more particularly, to static shroud assemblies for rotor blade arrays.BACKGROUND OF THE ART[0002]Typically, an axial gap is provided between a turbine shroud and the outer wall of a gas path duct at ambient temperatures, to allow for thermal expansion of the duct and / or the turbine shroud at engine operating temperatures. The magnitude of such thermal expansion can be predicted, and the gap sized, so that thermal expansion generally seals the gap to prevent leakage through the gap.[0003]However, the seal is not perfect and it must be ensured to adequately purge the adjacent cavity with sufficient cooling air to avoid hot gas ingestion. Reducing such uses of secondary air can increase gas turbine engine efficiency.[0004]Accordingly, there is a need for an improved turbine shroud sealing arrangement.SUMMARY[0005]In one aspect, there is provided a shroud sealing arrangement for a gas turbine engine, the ...

Claims

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Application Information

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IPC IPC(8): F01D25/12F01D9/04F01D11/08
CPCF01D25/12F01D11/08F01D9/041F05D2220/32F05D2260/201F05D2240/12F05D2240/30F05D2240/55F05D2260/202F05D2240/11F01D11/005Y02T50/60
Inventor LEFEBVRE, GUYPAQUET, RENE
Owner PRATT & WHITNEY CANADA CORP